DE102018122535B4 - Planetary gear device and gas turbine engine - Google Patents

Abstract

Planetary gear device (30) for a turbomachine (10) with a planetary carrier (34) and at least one planetary gear (32) rotatably arranged on a carrier device (29), the planetary gear (32) being arranged in the axial direction between two planetary carrier regions (34A, 34B). is, with which at least one carrier device (29) is connected in a rotationally fixed manner, a wedge sleeve (25, 70) being arranged between the carrier device (29) and the planet carrier regions (34A, 34B), via which a press connection between the carrier device ( 29) and the planet carrier regions (34A, 34B), and wherein a sleeve (50, 74) is provided radially between at least one of the wedge sleeves (25, 70) and a planet carrier region (34A, 34B).

Description

The present disclosure relates to a planetary gear device for a turbomachine with a planetary carrier and at least one planetary gear rotatably arranged thereon, and to a gas turbine engine.

From the DE 10 2018 106 564 A1 a planetary gear with a planet carrier and a carrier element firmly connected to it is known. At least one planet gear is rotatably mounted on the carrier element. The carrier element engages radially in a bore of the planet carrier. A wedge sleeve is provided radially between the planet carrier and the carrier element. The wedge sleeve is in operative connection with an outer, substantially cylindrical jacket surface area with a cylindrical surface of the bore of the planet carrier and with an inner conical jacket area with an outer conical jacket surface area of the carrier element.

One from the EP 3 306 140 A1 Known planetary gear assembly includes a sun gear and a plurality of planetary gears in meshing engagement with the sun gear and with a ring gear. The planet gears are rotatably mounted on bearing pins in a planet carrier. The bearing pins are each arranged in bores in the planet carrier and each include a small, conical section. Additionally, the planetary gear assembly includes tapered sleeves each configured to press-fit between a radially inner wall surface of the bore and a radially outer surface of each axially tapered portion of the bearing pin.

A two-piece combination of planetary hub and output shaft of a planetary reduction gear drive assembly is in the US 5,863,272 A described.

The present disclosure is based on the object of providing a planetary gear device that is characterized by a long service life and is easy to assemble, as well as a gas turbine engine designed with such a planetary gear device.

According to a first aspect, a planetary gear device for a turbomachine is provided with a planet carrier and with at least one planet gear rotatably arranged on a carrier device connected in a rotationally fixed manner to the planet carrier. The planet gear is arranged in the axial direction between two planet carrier regions, to which at least one carrier device is connected in a rotationally fixed manner. The planetary gear is rotatably mounted on the carrier device. A wedge sleeve is arranged between the carrier device and the planet carrier areas, via which a press connection is established between the carrier device and the planet carrier areas. In addition, a sleeve is provided radially between at least one of the wedge sleeves and a planet carrier area.

This ensures that even with a one-piece design of the planet carrier, a diameter area of the carrier device can be mounted axially between the two planet carrier areas, the diameter of which is larger than the diameter of the areas of the carrier device with which the carrier device engages in the planet carrier areas.

This offers the possibility of using carrier devices of the same structural design both in a one-piece and in a multi-part design of the planet carrier and thus producing the planetary gear device with low manufacturing costs.

It can be provided that the wedge sleeve is at least partially in operative connection with an outside and an inside of the sleeve. The outside of the wedge sleeve and the inside of the sleeve can be coordinated with one another in such a way that assembly of the wedge sleeve between the sleeve and the carrier device is simplified and a rotation-proof connection between the planet carrier area and the carrier device can be ensured.

If the wedge sleeve is at least partially in operative connection with an inside with an outside of the carrier device and the inside of the wedge sleeve and the outside of the carrier area are coordinated with one another, assembly of the planetary gear device can be carried out in a simple manner and the desired rotation-proof connection between the carrier device and The planet carrier can be produced to the required extent.

If the outside and/or the inside of the wedge sleeve is or are at least partially conical or cylindrical, the wedge sleeve can be positioned with low joining forces between the sleeve and the carrier device.

The inside of the sleeve can be conical or cylindrical, at least in some areas, in order to be able to assemble the sleeve and the wedge sleeve with low joining forces.

According to a further aspect, the sleeve has an outside at least in some areas with an inside of the planet carrier area in operative connection.

According to a further aspect, an outer diameter of the end face of the sleeve is larger than the diameter of the end face of the carrier device and at least the surface area of the end face of the sleeve that radially encompasses the end face of the carrier device is made of a non-sparking material.

The sleeve is thus designed with an axial contact surface for the planetary gear rotatably mounted on the carrier device. In addition, the spark-free material in the area of the contact surface of the sleeve for the planetary gear ensures that the formation of sparks is prevented when the planetary gear or its bearing rests on the end face of the sleeve. This in turn reduces the risk of fire within a jet engine of an aircraft in a structurally simple manner.

If the sleeve between the planet carrier regions rests at least in some areas with an end face on an end face of the carrier device, a load path is closed in a simple manner by the carrier device during an insertion process of the wedge sleeve between the sleeve and the carrier device. This means that deformations or deflections of the planet carrier areas during the insertion process of the wedge sleeve are avoided or reduced in a structurally simple manner.

Depending on the respective application, it can be provided that the end face of the sleeve, which is made with the spark-free material, and the end face of the sleeve, with which the sleeve rests on the end face of the carrier device, lie in a common axial plane. In addition, there is the possibility that the end face of the sleeve, which interacts with the end face of the carrier device, protrudes axially relative to the end face of the sleeve provided as a contact surface with a smaller outer diameter and the sleeve is designed to be stepped in its area facing the end face of the carrier device.

In a further embodiment of the planetary gear device, the sleeve has a radially outwardly pointing annular collar, the outer diameter of which is larger than the diameter of the inside of the planet carrier area, with which the outside of the sleeve is in operative connection. The annular collar of the sleeve forms a stop in the axial direction in a structurally simple manner, via which movement of the sleeve in the axial direction of insertion of the sleeve into the planet carrier area is limited.

According to a further aspect, the sleeve rests against the side surface of the planet carrier area with an end face of the ring collar facing a side surface of the planet carrier area, which means that the sleeve is additionally secured against rotation relative to the planet carrier area due to the frictional connection prevailing between the end face of the ring collar and the side surface.

A positive connection can be provided between the end face of the ring collar and the side surface of the planet carrier area, via which a relative rotational movement between the planet carrier area and the sleeve is at least partially blocked.

For this purpose, it can be provided, for example, that on the front side of the ring collar there is a nose, bead or the like which projects beyond the front side and which engages in a corresponding recess in the side surface of the planet carrier area with a corresponding clearance fit. The clearance fit ensures that the positive connection between the sleeve and the planet carrier area can be produced in a simple manner during assembly of the planetary gear device.

According to a further aspect, the outer diameter of the outside of the sleeve and the inner diameter of the inside of the planet carrier area interacting with the sleeve are coordinated with one another in such a way that there is an interference fit between the sleeve and the carrier device before the wedge sleeve is installed.

The excess fit can be in the range between 10 µm and 40 µm, preferably 20 µm to 30 µm, for example 25 µm. This in turn ensures that the sleeve can be inserted into the planet carrier area with comparatively low joining forces and, on the other hand, is attached to the planet carrier area to a defined extent and remains in the assembled position during assembly of the wedge sleeve.

According to a further aspect, the further wedge sleeve is at least partially in operative connection with an outside with an inside of a further sleeve or directly with an inside of the associated planet carrier area. In addition, the outside of the wedge sleeve and the inside of the sleeve or the inside of the planet carrier area are coordinated with one another. This means that the sleeve and/or the wedge sleeve can be assembled with comparatively low joining forces th can be carried out and the rotation-proof connection between the planet carrier and the carrier device can be established.

According to a further aspect, assembly is simplified if the inside of the further sleeve and/or the inside of the planet carrier area is/are at least partially conical or cylindrical.

In further embodiments of the planetary gear device, the planet carrier is designed in one piece or in several parts.

As noted elsewhere herein, the present disclosure may relate to a gas turbine engine. Such a gas turbine engine may include an engine core that includes a turbine, a combustion chamber, a compressor, and a core shaft connecting the turbine to the compressor. Such a gas turbine engine may include a fan (with fan blades) positioned upstream of the engine core.

Arrangements of the present disclosure may be particularly, but not exclusively, advantageous for gear driven fans. Accordingly, the gas turbine engine may include a gearbox that receives input from the core shaft and delivers drive to the fan for driving the fan at a lower speed than the core shaft. The input for the gearbox can come directly from the core shaft or indirectly from the core shaft, for example via a spur shaft and/or a spur gear. The core shaft may be rigidly connected to the turbine and compressor so that the turbine and compressor rotate at the same speed (with the fan rotating at a lower speed). The transmission can be designed as a planetary gear device described in more detail above.

The gas turbine engine described and claimed herein may have any suitable general architecture. For example, the gas turbine engine may include any desired number of shafts connecting turbines and compressors, such as one, two, or three shafts. By way of example only, the turbine connected to the core shaft can be a first turbine, the compressor connected to the core shaft can be a first compressor, and the core shaft can be a first core shaft. The engine core may further include a second turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor. The second turbine, the second compressor, and the second core shaft may be arranged to rotate at a higher speed than the first core shaft.

In such an arrangement, the second compressor may be positioned axially downstream of the first compressor. The second compressor may be arranged to receive flow from the first compressor (e.g., receive directly, for example, via a generally annular channel).

The transmission may be arranged to be driven by the core shaft configured to rotate (e.g. in use) at the lowest speed (e.g. the first core shaft in the example above). For example, the transmission may be arranged to be driven only by the core shaft configured to rotate (e.g. in use) at the lowest speed (e.g. only by the first core shaft and not the second core shaft in the example above). become. Alternatively, the transmission may be arranged to be driven by one or more shafts, for example the first and/or the second shaft in the above example.

According to a further aspect, a method for producing the planetary gear device described in more detail above is proposed. A position of the inside of the planet carrier area is determined and when a deviation of the determined position from a predefined position is detected, the inside and/or the outside of the sleeve is/are manufactured depending on the deviation.

As a result, manufacturing tolerances in the area of the planet carrier can be compensated for in a simple manner and the manufacturing costs of the planetary gear device can be reduced with little effort compared to conventionally manufactured planetary gear devices. Furthermore, due to the more precise positioning of the planet gears in the planet carrier relative to one another, the planetary gear device can be designed with a lower component weight and can be operated with a higher degree of efficiency, since a desired rolling behavior can be ensured in the area of the tooth meshing of the planetary gear device.

A joining force can be kept constant or varied during the insertion of the sleeve into the planet carrier area and/or during the insertion of the wedge sleeve into the planet carrier area or into the sleeve.

The planet carrier area can be inserted before inserting the sleeve and/or the wedge sleeve Heated in relation to an ambient temperature and / or the sleeve and / or the wedge sleeve are cooled in relation to the ambient temperature in order to be able to insert the sleeve and / or the wedge sleeve with low joining forces.

Furthermore, it can be provided that during the insertion of the wedge sleeve between the planet carrier area and the carrier element or between the sleeve and the carrier element, oil under pressure between the outside of the wedge sleeve and the inside of the sleeve or the inside of the planet carrier area and / or between the Inside of the wedge sleeve and the outside of the carrier device is initiated.

• 1 eine Längsschnittansicht eines Gasturbinentriebwerks;
• 2 eine vergrößerte Teillängsschnittansicht eines stromaufwärtigen Abschnitts eines Gasturbinentriebwerks;
• 3 eine Alleindarstellung eines Getriebes für ein Gasturbinentriebwerk;
• 4 eine Teillängsschnittansicht eines Planetenträgers, einer Trägereinrichtung, einer Keilhülse und einer Hülse des Getriebes gemäß 3 in montiertem Zustand;
• 5 eine 4 entsprechende Darstellung des Planetenträgers, der Trägereinrichtung, der Hülse und der Keilhülse, wobei eine Innenseite der Hülse und eine Außenseite der Keilhülse konusförmig ausgeführt sind;
• 6 eine 4 entsprechende Darstellung des Planetenträgers, der der Trägereinrichtung, der Hülse und der Keilhülse, wobei eine Innenseite der Keilhülse und eine Außenseite der Trägereinrichtung wenigstens annähernd zylinderförmig ausgeführt sind;
• 7 eine 4 entsprechende Darstellung des Planetenträgers, der Trägereinrichtung, der Hülse und der Keilhülse, wobei die Hülse in einer der Trägereinrichtung zugewandten Stirnfläche mit einem funkenfreien Material ausgebildet ist;
• 8 eine stark schematisierte Teildarstellung des Planetenträgers, der Trägereinrichtung sowie der Hülse und zwei Keilhülsen in vollständig montiertem Zustand, in dem über die Keilhülsen eine drehfeste Verbindung zwischen dem Planetenträger und der Trägereinrichtung hergestellt ist; und
• 9 eine 8 entsprechende Darstellung des Planetenträgers, des Trägerelementes, der Hülse und einer weiteren Hülse sowie der Keilhülsen, wobei eine der Keilhülsen lediglich in teilmontiertem Zustand gezeigt ist.

Embodiments will now be described by way of example with reference to the figures; show in the figures:

• 1 a longitudinal sectional view of a gas turbine engine;
• 2 an enlarged partial longitudinal sectional view of an upstream portion of a gas turbine engine;
• 3 a sole representation of a gearbox for a gas turbine engine;
• 4 a partial longitudinal section view of a planet carrier, a carrier device, a wedge sleeve and a sleeve of the transmission according to 3 in assembled condition;
• 5 one 4 corresponding representation of the planet carrier, the carrier device, the sleeve and the wedge sleeve, with an inside of the sleeve and an outside of the wedge sleeve being conical;
• 6 one 4 corresponding representation of the planet carrier, the carrier device, the sleeve and the wedge sleeve, an inside of the wedge sleeve and an outside of the carrier device being at least approximately cylindrical;
• 7 one 4 Corresponding representation of the planet carrier, the carrier device, the sleeve and the wedge sleeve, the sleeve being formed with a non-sparking material in an end face facing the carrier device;
• 8th a highly schematic partial representation of the planet carrier, the carrier device as well as the sleeve and two wedge sleeves in a fully assembled state, in which a rotation-proof connection is established between the planet carrier and the carrier device via the wedge sleeves; and
• 9 one 8th Corresponding representation of the planet carrier, the carrier element, the sleeve and another sleeve as well as the wedge sleeves, with one of the wedge sleeves only being shown in a partially assembled state.

1 represents a gas turbine engine 10 or a turbomachine with a main axis of rotation 9. The engine 10 includes an air inlet 12 and a thrust fan 23, which generates two air flows: a core air flow A and a bypass air flow B. The gas turbine engine 10 includes a core 11 or an engine core , which absorbs the core air flow A. The engine core 11 includes, in axial flow order, a low-pressure compressor 14, a high-pressure compressor 15, a combustion device 16, a high-pressure turbine 17, a low-pressure turbine 19 and a core thrust nozzle 20. An engine nacelle 21 surrounds the gas turbine engine 10 and defines a bypass channel 22 and a bypass thrust nozzle 18. The bypass air flow B flows through the bypass channel 22. The fan 23 is attached to the low-pressure turbine 19 via a shaft 26 and an epicycloid gear 30 and is driven by it. The shaft 26 is also referred to as a core shaft or a connecting shaft.

In use, the core air flow A is accelerated and compressed by the low-pressure compressor 14 and fed into the high-pressure compressor 15, where further compression occurs. The compressed air expelled from the high pressure compressor 15 is directed into the combustion device 16 where it is mixed with fuel and the mixture is burned. The resulting hot combustion products then propagate through and thereby drive the high pressure and low pressure turbines 17, 19 before being expelled through the nozzle 20 to provide some thrust. The high-pressure turbine 17 drives the high-pressure compressor 15 through a suitable connecting shaft or shaft 27, which is also referred to as a core shaft. The fan 23 generally provides the majority of the thrust force. The epicycloid gear 30 is a reduction gear.

An exemplary arrangement for a geared fan gas turbine engine 10 is shown in 2 shown. The low-pressure turbine 19 (see 1 ) drives the shaft 26, which is coupled to a sun gear 28 of the epicycloidal gear assembly 30. A plurality of planet gears 32, which are coupled to one another by a planet carrier 34, are located radially outside of the sun gear 28 and mesh with it and are each rotatably arranged on carrier devices 29 which are non-rotatably connected to the planet carrier 34. The planet carrier 34 restricts the planet gears 32 from rotating synchronously around the sun gear 28 while allowing each planet gear 32 to move onto the carrier devices 29 can rotate around its own axis. The planet carrier 34 is coupled to the fan 23 via linkage 36 to drive its rotation about the engine axis 9. An external gear or ring gear 38, which is coupled to a stationary support structure 24 via linkage 40, is located radially outside of the planet gears 32 and meshes with it.

It is noted that the terms “low pressure turbine” and “low pressure compressor” as used herein may be construed to mean the lowest pressure turbine stage and the lowest pressure compressor stage, respectively (i.e., not the fan 23) and/or the turbine and compressor stages interconnected by the lowest speed shaft 26 in the engine (i.e. not including the transmission output shaft that drives the fan 23). In some literature, the “low pressure turbine” and “low pressure compressor” referred to herein may alternatively be known as the “medium pressure turbine” and “medium pressure compressor”. Using such alternative nomenclature, the blower 23 may be referred to as a first compression stage or lowest pressure compression stage.

The epicycloid gear 30 is in 3 shown in more detail as an example. The sun gear 28, the planetary gears 32 and the ring gear 38 each include teeth around their periphery for meshing with the other gears. However, for the sake of clarity, only exemplary sections of the teeth are shown in 3 shown. Although four planetary gears 32 are illustrated, it will be apparent to those skilled in the art that more or fewer planetary gears 32 may be provided within the scope of the claimed invention. Practical applications of an epicycloidal gear 30 generally include at least three planet gears 32.

This in 2 and 3 Epicycloidal gear 30 shown as an example is a planetary gear device in which the planet carrier 34 is coupled to an output shaft via linkage 36, with the ring gear 38 being fixed. However, any other suitable type of epicycloidal gear 30 may be used. As another example, the epicycloidal gear 30 may have a star arrangement in which the planet carrier 34 is held fixed while allowing the ring gear (or outer gear) 38 to rotate. With such an arrangement, the fan 23 is driven by the ring gear 38. As another alternative example, the transmission 30 may be a differential gear in which both the ring gear 38 and the planet carrier 34 are allowed to rotate.

It is understood that the in 2 and 3 The arrangement shown is merely exemplary and various alternatives are within the scope of the present disclosure. By way of example only, any suitable arrangement for positioning the transmission 30 in the engine 10 and/or for connecting the transmission 30 to the engine 10 can be used. As another example, the connections (e.g. the linkages 36, 40 in the example of 2 ) between the transmission 30 and other parts of the engine 10 (such as the input shaft 26, the output shaft and the fixed structure 24) have some degree of rigidity or flexibility. As a further example, any suitable arrangement of bearings between rotating and stationary parts of the engine (e.g., between the input and output shafts of the transmission and fixed structures such as the transmission housing) may be used and is not disclosed to the exemplary arrangement of 2 limited. For example, it will be readily apparent to those skilled in the art that the arrangement of output and support linkages and bearing positioning in a star arrangement (described above) of the transmission 30 is generally different from those exemplified in 2 shown would differ.

Accordingly, the present disclosure extends to a gas turbine engine with any arrangement of gear types (e.g., star or planetary), support structures, input and output shaft arrangements, and bearing positionings.

Optionally, the transmission can drive auxiliary and/or alternative components (e.g. the medium-pressure compressor and/or a booster compressor).

Other gas turbine engines to which the present disclosure may apply may have alternative configurations. For example, such engines can have an alternative number of compressors and/or turbines and/or an alternative number of connecting shafts. As another example, this shows in 1 Gas turbine engine shown has a split flow nozzle 20, 22, which means that the flow through the bypass channel 22 has its own nozzle, which is separate from the engine core nozzle 20 and radially outward thereof. However, this is not limiting, and any aspect of the present disclosure may also apply to engines in which the flow through the bypass passage 22 and the flow through the core 11 are prior to (or upstream of) a single nozzle, which is referred to as a mixed flow nozzle can be referred to, mixed or combined. One or both nozzles (whether mixed or split stream) may have a fixed or variable range. For example, although the example described relates to a turbofan engine, the disclosure may apply to any type of gas turbine engine, such as a gas turbine engine. B. with an open rotor (where the fan stage is not surrounded by an engine nacelle) or a turboprop engine.

The geometry of the gas turbine engine 10 and components thereof are defined by a conventional axis system having an axial direction (aligned with the axis of rotation 9), a radial direction (in the bottom-up direction). 1 ) and a circumferential direction (perpendicular to the view in 1 ). The axial, radial and circumferential directions are perpendicular to each other.

4 shows a partial sectional view of the planet carrier 34 or a planet carrier area 34A, a wedge sleeve 25 and the essentially hollow cylindrical carrier device 29, on which a planet gear 32 can be rotatably arranged and which is rotationally fixed in the manner described in more detail below via the wedge sleeve 25 and a sleeve 50 connected to the planet carrier 34.

The sleeve 50 is arranged radially between the wedge sleeve 25 and the planet carrier area 34A and is in operative connection in areas with an outside 51 with an inside 52 of a bore 53 of the planet carrier area 34A.

An inside 54 of the sleeve 50 is in turn engaged with an outside 55 of the wedge sleeve 25. In addition, the wedge sleeve 25 rests with an inside 56 on an outside 57 of the carrier device 29.

It is provided that each of the planet gears 32 of the planetary gear 30 is rotatably arranged on a separate carrier device 29 and that each carrier device 29 has a wedge sleeve 25 at the end with planet carrier regions 34A of the planet carrier that are spaced apart from one another in the axial direction of the planetary gear 30 and are firmly connected to one another 34 is in an operative connection in a rotationally fixed manner. The carrier devices 29 are, for example, tapered in the area of their two ends and interact with these end regions via a respective wedge sleeve 25 and a respective sleeve 50 with the planet carrier regions 34A of the planet carrier 34.

Since the wedge sleeves 25 and the planet carrier regions 34A of the planet carrier 34 that interact with them and the carrier devices 29 in the in 4 illustrated embodiment are essentially the same, the structural design of the planetary gear 30 and the establishment of the non-rotatable connection between the carrier devices 29 and the planet carrier 34 are initially based on the illustration 4 explained in more detail.

The course of the inside diameter D56 of the inside 56 of the wedge sleeve 25 and the course of the outside diameter D57 of the outside 57 of the carrier device 29 are coordinated with one another in such a way that in the fully assembled operating state of the wedge sleeve 25 in the overlap area between the conical inside 56 of the wedge sleeve 25 and the conical or .Conical outside 57 of the carrier device 29 there is an interference fit. The interference fit is such that a rotationally fixed connection between the carrier device 29 and the planet carrier 34 is established in any case by the wedge sleeve 25.

In addition, the course of the outer diameter D51 of the presently cylindrical outside 51 of the sleeve 50 and the course of the inside diameter D52 of the also cylindrical inside 52 of the planet carrier area 34A are coordinated with one another in such a way that in the fully assembled operating state of the sleeve 50 in the overlap area between the planet carrier area 34A and the sleeve 50 has an interference fit, the interference fit in this area being less than the interference fit between the wedge sleeve 25 and the carrier device 29.

The sleeve 50 has a radially outwardly pointing annular collar 58, the outer diameter D58 of which is larger than the diameter D52 of the inside 52 of the planet carrier area 34A, with which the outside 51 of the sleeve 50 is in operative connection. This means that there is also an overlap area in the radial direction between the sleeve 50 and the planet carrier area 34A.

An axial distance between an end face 59 of the sleeve 50 and an end face 60 of the annular collar 58 of the sleeve 50 facing the planet carrier area 34A is in the case in 4 illustrated embodiment designed so that the sleeve with its end face 59 rests on an end face 61 of the carrier device 29 and at the same time the end face 60 rests on a side surface 62 of the planet carrier area 34A without play or as far as possible without play.

This ensures that when installing the wedge sleeve 25 between the sleeve 50 and the trä ger device 29 the power flow of the joining force is closed both through the planet carrier 34 and through the carrier device 29 and undesirable bending of the planet carrier area 34A is limited or completely avoided.

Deviating from this, there is also the possibility that the axial distance between the end face 59 and the side surface 60 is such that the sleeve 50 rests with its end face 59 against the end face 61 of the carrier device 29 without play, while the side face 60 of the annular collar 58 in the axial direction is slightly spaced from the side surface 62 of the planet carrier area 34A.

An outer diameter D29 of the carrier device 29 is smaller than the inner diameter D52 of the inside 52 of the planet carrier region 34A, which means that the carrier device 29 can be arranged in areas between the two planet carrier regions 34A to the desired extent, even with a one-piece design of the planet carrier 34.

Furthermore, there is also the possibility that the sleeve 50 is designed without the annular collar 58 and the sleeve 50 is designed with a constant outer diameter D51 between the end face 59 and its opposite end face 63.

5 until 7 show further embodiments of the planetary gear device 30 in each case 4 corresponding representation. The following description will only focus on the differences from the design of the planetary gear device 30 according to 4 discussed and the description regarding the further functioning of the planetary gear device 30 4 referred.

When designing the planetary gear device 30 according to 5 Both the inside 56 of the wedge sleeve 25 and its outside 55 are each conical or conical, with the outer diameter D55 and the inner diameter D56 of the wedge sleeve 25 increasing steadily starting from the end face 64 facing the support device 29 in the direction of the opposite end face 65. The wedge sleeve 25 can thus be inserted in a simple manner between the outside 57 of the carrier device 29 and the inside 54 of the sleeve 50, which is also conical or conical, in order to produce the rotationally fixed connection between the carrier device 29 and the planet carrier 34.

Deviating from this is the case with the planetary gear device 30 6 only the outside 55 of the wedge sleeve 25 is conical or conical, while the inside 56 of the wedge sleeve 25 is cylindrical.

At the in 7 In the embodiment of the planetary gear device 30 shown, the outer diameter D51 of the outer side 51 of the sleeve 50 is larger by a defined amount than the outer diameter D29 of the carrier device 29. The end face 59 of the sleeve 50 is at least in the annular surface area of the end face 59, which is not in contact with the End face 61 of the carrier device 29 is made with a material that does not generate any sparks in the event of frictional contact with an end face 66 of the planetary gear 32 facing the sleeve 50. This prevents the ignition of flammable fluid in the area of the planetary gear device 30. In addition, a coefficient of friction of the material in this area of the end face 59 of the sleeve 50 is low, so that the planetary gear 32 is only braked to a small extent when the end face 66 of the planetary gear 32 rests on the end face 59 of the sleeve 50.

8th shows, in addition to the planet carrier area 34A, a further planet carrier area 34B of the planet carrier 34, which is spaced apart in the axial direction and in which the carrier device 29 is arranged. In order to establish a rotation-proof connection between the planet carrier area 34B and the carrier device 29, a further wedge sleeve 70 is inserted between an inside 67 of a bore 68 of the planet carrier area 34B and an outside 69 of the carrier device 29. A corresponding interference fit is provided between an inside 71 of the further wedge sleeve 70 and the outside 69 of the carrier device 29.

The planet carrier area 34B lies in the area of its inner side surface 72 on an end face 73 of the carrier device 29 without play. This means that the joining force applied during the joining process of the further wedge sleeve 70 between the planet carrier region 34B and the carrier device 29 is introduced into the planetary carrier region 34B and supported by the carrier device 29 to the desired extent, and deformations or bends are caused during the assembly of the further wedge sleeve 70 Area of the planet carrier area 34B in the axial direction of the carrier device 29 is avoided in a structurally simple manner.

This also differs from the in 9 illustrated embodiment of the planetary gear device 30 between the further wedge sleeve 70 and the planet carrier area 34B, a further sleeve 74 is arranged, the structural design of which essentially corresponds to the structural design of the sleeve 50 4 corresponds and the single is designed to be a mirror image of this. The further sleeve 74 is in 9 shown in its fully assembled state, while the sleeve 50 is not yet in its fully assembled position.

Again deviating from this, in a further embodiment of the planetary gear device 30 it can be provided that the sleeve 50 is in the in 9 The position shown is already in its fully assembled end position and projects beyond the outside 62 of the planet carrier area 34B and the end face 63 of the sleeve 50 in the axial direction.

During assembly of the sleeve 50, the joining force F is applied to it in the area of its end face 63 in the axial direction or in the insertion direction. The planet carrier area 34A is supported in the area of the end face 61 facing away from the end face 73 of the carrier device 29. This avoids undesirable deformations of the planet carrier 34 or in the area of the two planet carrier regions 34A and 34B.

The arrangement of the sleeve 50 and / or the further sleeve 74 in the bores 53 and 68 of the planet carrier areas 34A and 34B offers the possibility of dismantling the planetary gear device 30 during maintenance of the gas turbine engine 10 without loading the planet carrier 34 to any significant extent . This results from the fact that when dismantling the carrier device 29, only the wedge sleeves 25 and 70 have to be moved out of engagement with the carrier device 29 and the sleeves 50 and 74. Subsequently, the sleeves 50 and 74, which are each arranged in the planet carrier 34 with a significantly smaller interference fit, are to be removed from the planet carrier areas 34A and 34B, with significantly lower release forces having to be applied for this.

If damage is caused in the area of the inside 52 and 67 of the bores 53 and 68 during dismantling of the sleeves 50 and 74, this can be remedied in a simple manner by appropriate post-processing of the inside of the bores 53 and 68 of the planet carrier areas 34A and 34B A correspondingly adapted sleeve can later be arranged in the planet carrier areas 34A and 34B with little effort.

As a result, the service life of the planet carrier 34, which is characterized by high manufacturing costs compared to the other components of the planetary gear device 30, can be extended with little effort.

Furthermore, the use of the sleeves 50 and 74 also offers the possibility of eliminating deviations caused by manufacturing inaccuracies between a predefined position of the bores 53 and 68 of the planet carrier regions 34A and 34B from a predefined position by correspondingly adapted production of the outer sides 51 and/or the inner sides 54 of the sleeves 50 and 74. As a result, the tooth meshing between the planet gears 34 of the planetary gear device 30 and the sun gear 28 and the ring gear 38 can be improved, which in turn has a positive effect on the service life of the planetary gear device 30. In addition, this also makes it possible to design the components of the planetary gear device 30 with lower strengths, which means that the planetary gear device 30 can be designed with a low dead weight.

Reference character list

9

Main axis of rotation

10

Gas turbine engine

11

core

12

Air intake

14

Low pressure compressor

15

High pressure compressor

16

Combustion device

17

High pressure turbine

18

Bypass thrust nozzle

19

Low pressure turbine

20

Core thruster

21

Engine nacelle

22

Bypass channel

23

fan

24

Support structure

25

wedge sleeve

26

Wave, core wave

27

Wave

28

sun gear

29

Carrier facility

30

Gearbox, planetary gear device

32

Planetary gear

34

Planet carrier

34A, 34B

Planet carrier area

36

linkage

38

ring gear

40

linkage

50

sleeve

51

Outside of the sleeve

52

Inside of the bore of the planet carrier area 34A

53

Bore of the planet carrier area 34A

54

Inside of the sleeve 50

55

Outside of the wedge sleeve 25

56

Inside of the wedge sleeve 25

57

Outside of the carrier device 29

58

50 sleeve ring collar

59

Front side of the sleeve 50

60

Front side of the ring collar 58

61

Front side of the carrier device 29

62

side surface

63

Front side of the sleeve 50

64

Front side of the wedge sleeve 25

65

Front side of the wedge sleeve 25

66

Front side of the planet gear 32

67

Inside of the planet carrier area 34B

68

Bore of the planet carrier area 34B

69

Outside of the carrier device 29

70

another wedge sleeve

71

Inside of the additional wedge sleeve 70

72

inner side surface of the planet carrier area 34B

73

Front side of the carrier device 29

74

another sleeve

75

line

A

Core airflow

b

Bypass airflow

D29

Outer diameter of the carrier device 29

D51

Outer diameter of the outside 51 of the sleeve 50

D52

Inner diameter of the inside 52 of the planet carrier area 34A

D55

Outer diameter of the outside 55 of the wedge sleeve 25

D56

Inner diameter of the inside 56 of the wedge sleeve 25

D57

Outer diameter of the outside 57 of the carrier device 29

D58

Outer diameter of the ring collar 58

F

joining force

Claims (17)

Planetary gear device (30) for a turbomachine (10) with a planetary carrier (34) and at least one planetary gear (32) rotatably arranged on a carrier device (29), the planetary gear (32) being arranged in the axial direction between two planetary carrier regions (34A, 34B). is, with which at least one carrier device (29) is connected in a rotationally fixed manner, a wedge sleeve (25, 70) being arranged between the carrier device (29) and the planet carrier regions (34A, 34B), via which a press connection between the carrier device ( 29) and the planet carrier regions (34A, 34B), and wherein a sleeve (50, 74) is provided radially between at least one of the wedge sleeves (25, 70) and a planet carrier region (34A, 34B). Planetary gear device according to Claim 1 , characterized in that the wedge sleeve (25, 70) is at least partially in operative connection with an outside (55) with an inside (54) of the sleeve (50, 74). Planetary gear device according to Claim 1 or 2 , characterized in that the wedge sleeve (25, 70) is at least partially in operative connection with an inside (56) with an outside (57) of the carrier device (29). Planetary gear device according to Claim 3 , characterized in that the outside (55) and/or the inside (56) of the wedge sleeve (25, 70) is/are at least partially conical or cylindrical. Planetary gear device according to one of the Claims 2 until 4 , characterized in that the inside (54) of the sleeve (50, 74) is at least partially conical or cylindrical. Planetary gear device according to one of the Claims 1 until 5 , characterized in that the sleeve (50, 74) has an outside (51) with an inside (52) at least in some areas. of the planet carrier area (34A, 34B) is in operative connection. Planetary gear device according to one of the Claims 1 until 6 , characterized in that an outer diameter (D51) of an end face (59) of the sleeve (50, 74) is larger than the diameter (D29) of an end face (61) of the carrier device (29) and at least the end face (61) of the carrier device (29) radially encompassing surface area of the end face (59) of the sleeve (50, 74) is made of a non-sparking material. Planetary gear device according to one of the Claims 1 until 7 , characterized in that the sleeve (50, 74) between the planet carrier regions (34A, 34B) rests at least partially with an end face (59) on an end face (61) of the carrier device (29). Planetary gear device according to Claim 7 or 8th , characterized in that the sleeve (50, 74) has a radially outwardly facing annular collar (58), the outer diameter (D58) of which is larger than the diameter (D52) of the inside (52) of the planet carrier area (34A, 34B). which the outside (51) of the sleeve (50, 74) is in operative connection. Planetary gear device according to Claim 9 , characterized in that the sleeve (50, 74) rests on the side surface (62) of the planet carrier region (34A, 34B) with an end face (60) of the annular collar (58) facing a side surface (62) of the planet carrier region (34A, 34B). . Planetary gear device according to Claim 10 , characterized in that between the end face (60) of the annular collar (58) and the side surface (62) of the planet carrier area (34A, 34B) a positive connection is provided at least in some areas, via which a relative rotational movement between the planet carrier area and (34A, 34B) of the sleeve (50, 74) is at least partially blocked. Planetary gear device according to one of the Claims 6 until 11 , characterized in that the outside diameter (D51) of the outside (51) of the sleeve (50, 74) and the inside diameter (D52) of the inside (52) of the planet carrier area (34A, 34B) cooperating with the sleeve (50, 74) are as follows are coordinated with one another so that there is an interference fit between the sleeve (50, 74) and the planet carrier area (34A, 34B) before assembly of the wedge sleeve (25, 70) between the sleeve (50, 74) and the carrier device (29). Planetary gear device according to one of the further Claims 1 until 12 , characterized in that the further wedge sleeve (70) is at least partially in operative connection with an outside with an inside of a further sleeve (74) or directly with an inside of the associated planet carrier area (34B). Planetary gear device according to Claim 13 , characterized in that the inside of the further sleeve (74) and / or the inside of the planet carrier area (34B) is/are at least partially conical or cylindrical. Planetary gear device according to one of the Claims 1 until 14 , characterized in that the planet carrier (34) is designed in one piece or in several parts. A gas turbine engine (10) for an aircraft, comprising: a core (11) comprising a turbine (19), a compressor (14) and a shaft (26) connecting the turbine (19) to the compressor (14); a fan (23) positioned upstream of the engine core (11), the fan comprising a plurality of cores (11); and a gearbox (30) receiving input from the core shaft (26) and providing drive to the fan (23) for driving the fan (23) at a lower speed than the shaft (26), the gearbox (30) as a planetary gear device according to one of Claims 1 until 15 is executed. Gas turbine engine Claim 16 , characterized in that the turbine is a first turbine (19), the compressor is a first compressor (14) and the core shaft is a first shaft (26); the engine core (11) further comprises a second turbine (17), a second compressor (15) and a second shaft (27) connecting the second turbine to the second compressor; and the second turbine (17), the second compressor (15) and the second shaft (27) are arranged to rotate at a higher speed than the first shaft (26).

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